| 摘要 |
<p>In a gas turbine engine, it is known to have a main air intake, ore or tore combustion chambers, a compressor, a turbine, a bypass fan, and an inner and outer exhaust assembly. This invention has the following distinguishing features: The compressor turbine and by-pass fan are compoments of a common wheel. One or more combustion chambers having a U-shape are located upstream of the wheel in the main air intake where the(se) combustion chamber(s) are fed air from the compressor and expel expanding gases through an open ended turbine. The exhaust ports(s) of the expanding gases drive only part of the turbine blades, allowing air from the main air intake to pass through the turbine, thereby cooling them. No stator blades are required, as the cooling air being propelled through the turbine cause an opposite spiralling effect to the deflected exhaust gases. These new features will significantly reduce the complexity of the engine and allow the use of metals having a low resisting to heat, thereby avoiding the use of exotic heat resisting metal alloys, currently being used in gas turbine engines. This engine also has a self-starting capability without ancillary assists specifically designed for this purpose, which current gas turbines do not posses. The location of the combustion chamber(s) partially preheat combustion air, improving engine performance. This gas turbine engine will primarily be uses for the propulsion of missiles and aircraft.</p> |
